Spinner mounting



May

Filed A 1946 E. w. RADTKE SPINNER MOUNTIN 3 Sheets-Sheet 1 TTORNE May 31, 1949. E. w. RADTKE SPINNER MOUNTING 3 Sheets-Sheet 2 Filed Aug. 10, 1946 INVENTOR lZ'tZwarzZ 715304327? ATTORNEY a bil I Patented May 31, 1949 S OF F-liC Et SPINNER MOUNTING' EdwardW. Radtke, Hartford; C(mnz, assignoi' to United Aircraft" Corporation; East Hartford; Conn., a corporation of Delaware ApplicationrAugust's 10, 1946, Serial N 0. 689 -697 This: invention relates" to" propeller assemblies and more" particularly? to spinners such as are carried by the forward en'd'of the propeller shaft and serve as a cover fbrthehub of thepropeller;

Ithas been the" usual" practice" to vsupport the 5 splnnerish'ell directly. from" theipi'opeller hub a'djacentthetpropeller"shaft? Asa resultofth'e high stresses set up in the shell due to centrifugal forcesandhanding-momentsthismeans of supporting the shell has? not been entirelvsatisfactory, and in" the caseo'f large diameter spin- 11ers now coming into use'h'as provedinadequate.

Itiis an object of thepresent invention topro5 vid a propeller" assembly including an improved spinner and improved supporting structure 15 therefor:

Another object of thwinverition isto provide improved? spinner and spinner-"mounting means which-provide high strength-to resist loading due to forces and moments alongw'r" about the three comrdinateaxes-of-the propeller.

A fiir'ther" ohject of-the invention is to provide spinner supporting means aifordin'g firm support-for the cutouts" in "the shell through" which the propeller blades" pass to the-hub.-

Another object of the present invention is to provide a: spinner construction whicheasy 10" assemble on the. propeller arid which locates the spinner accurately relative to the axis of rotationoff the propeller withoutthemecessitv for ad justinentsin assembh;

A still further object ofthe'invention' is generany to improve the construction and operation of prop'el'ler' spinners:

Theseand otherobjects'and advantages ofthe inventiom will be apparent from the following" dtailed descr iption' of one erhlci'odirhel'it of the invention shown for' purpese's ofiillustration' in' the accompanyingdrawingsi In thesedr'awings i 7 Harris a side elevatimr of the forward end of amairplane: fuselage illustrating th'ei invention; partsz ofith'e lengine eowlingran'dw the spihner shell belng brokenfiaway 1 Figs i2: is a side e1evationl on -an enlarged scale imthe wicinity of the' spinnenthe propeller blades andiparttofi till-3 8111111161 sh'ell beirrg b'rokenv away;

Elg." 5""is avdetailed: perspective 1 view showing parts ofithespinner support; Cand Asihereimshowman" engine l 0 of tl'ie aircooled; radial type 1' drives a propell'r" shaft- IZ on which isimounted a propeller includinga hub= H and take diiot 21 leadirigsto the engine-compartmenti A spinnershelll encloses the propeller hub comprises three sections, adome-shaped nose. section 24',1a forwardannular'section 26 and" a Sections '26" and 28 of" thetspinner each of these" cutouts having inturned' beaded edges 36 "which closely surround" the'rblade shanks 38 but areout of contacttherewith. U

Section 2'6""of"the"spitizier."shellhas an" annular band 40" secured; as by riveting or" spot welding, to" its" inner surface" which" extends beyond the edgeof "thesh'ellt'oprovide" an annular seat for thenos'e"sebtioriendtenninates in an inturned' stiifning'flange portion. nose section 24 is secured to the annular'seat on section 2Bby7bo1ts 44 the heads of which are either rounded or"are"fiush with the outer surfa'ceofthe shelrsectionsi A series- 0f peripher- The rear portion of ally disposedfholes are providdin flange portion 4-2 in" which bolt and: washer"units"-4'6*'are suitably disposed as required to balance the spinner assembly. 7 V

It willbe noted that thedividing line lii between the front" andrear se'ctiohs" 26 and 28 of the spinner lies in a transverse plane which includesthe longitudinal ax es ofthe several propellrblades I6 and that" consequently the cutouts 3'4 in the two sectib'ns are semi-circular and are symmetrical with these blade axes. In accordance" with this invention improved means are'provided withinthe spinner for suitably conneoting the'forward' and rear sections 26 1 and 1 28 and for supporting the spinner in an improved manner in symmetrical position relative to the anisof rotation of thepropellerz As will b'e apparent from Fig; 4; the propeller hub l has' four equally spaced, radially directed blade shank receiving i liairrels lt terminating in internally"threadd end'sfio whiclrheretofore' receivedth'e'threadewend ofa; nut for compressing a p'aokin'g Washer 52 againsflan internal packing ring' 54'- adjacent? the" end of the barrel. In acooi'da'nce with this invention the'usual nut is" replaced by an extensiomsle'eva 56 provided with a-redi1ced externally threaded end which is re ceiv'ahle in tIieWhreaddportion 50' of the barre1- and is provided" with? an exposed spanner Wench engaging portion 58rorming a" shoulder 59 which abuts the end of the hub barrel and locates the sleeve accurately relative to the propeller axis. If desired, this shoulder may be in the form of a nut threaded on the portion 59 to allow for adjustment of the sleeve relative to the hub barrel. The inner threaded end of sleeve 56 serves in place of the former nut to compress the packing 54. The sleeves 56 extend radially substantially to the inner surface of spinner section 26, terminating just short of the inturned bead 36 at the forward portion of the cutouts. Each of the sleeves 56 is provided adjacent its outer extremity with a pair of spaced annular ribs 60 which have finished confronting faces accurately located relative to the shoulder 59. The grooves formed by the ribs all are utilized for accurately positioning the spinner relative to the axis of rotation of the propeller and for supporting the spinner shell. against centrifugal forces and against bending moments exerted about the three coordinate axes of the propeller.

To this end, annular clamping collars, gen erally indicated at 62, are provided about the extension sleeves 56 at each blade shank location. As shown most clearly in Fig. 5, these collars 62 comprise two complementary semi-circular members 64 and 66 having flanges E9 and 19 a pair of which are permanently secured, as by welding, to the adjacent inner surfaces of spinner sections 28 and 26, respectively, around each of the several cutouts. Each of the collar members 64 and 66 has a generally semi-circular key '52 permaness to permit the collars to firmly clamp the sleeves 56 while also clamping the webs 92, 94 between the lugs 18 and 80.

Midway between the blade shanks the flanges 96 and 98 are provided with widened portions N14 to accommodate one leg I06 of an angle clamp, the other leg I08 of which is secured to the Web.

' Bolt H extends through the leg H38 and the nently secured to its inner periphery. The keys 12 are rectangular in cross section and closely fit the groove between the ribs 66 so as to accurately locate the collar and accordingly the attached spinner sections radially on the barrel and sleeve extensions. The collar members 64 and 66 are also provided with integral bent ears M which extend laterally in planes parallel with the plane of the dividing line 48 between the shell sections 26 and. 28.

For the purpose of clamping the fore and aft collar members 64 and 66 about the extension sleeves 56, these members are provided with pairs of spaced parallel lugs 16 and 89 having curved attaching bases 62 which conform to the outer periphery of the annular collar members and are attached thereto by a row of rivets 84 which ex tend through the base of the collar members and also by a second row of rivets 66 which extend through the base, the collar and the underlying ring, or key, formed by members '52. Clamping bolts 88 extend through the lugs '58 and 86 and clamp the collar members 64, 66 firmly about sleeve extensions 56, it being noted that the key members 12 are slightly less than semi-circular so that there is a space 96 between the adjacent ends thereof in the clamped position of the collars.

The confronting peripheral portions of shell sections 26 and 28 are further reinforced and connected by flanged webs generally indicated at 92 and 94 (Fig. 6) which extend between and are connected with the clamping collars just described. The webs 92 and 94 have like arcuate flanges 96 and 98 which overlie the inner surfaces of the shell portions 26 and 28 and are permanently welded thereto. The inner edges of these web members are provided with rearwardly directed parallel stiffening flanges 99 and H10 as shown more clearly in Fig. 6. The web members 92, 94 extend between the lugs 18 and 8B of the clamping collars and have a filler member I62 therebetween which is of suitable thickwebs of members 92, 94 to provides additional clamping means midway between the clamping collars.

The flanges 96 and 98 are also provided with offset ends H2 which overlie the flanges 68 and T6 of the clamping collars and are secured thereto by rivets H 4. It will thus be evident that the front shell section 26 has permanently secured thereto one half of a clamping collar at each cutout and an intermediate web clamping member between adjacent collar members, while the rear section 28 has the complemental collar member and another parallel web member permanently secured thereto. By means of bolts 88 and I I6 the two shell sections 26 and 28 can thus be readily secured together about the intervening hub carried extension sleeves 56.

In order to gain access to the propeller hub it is only necessary to remove the screws 44 and the nose section 24 which permits removal of the propeller and spinner sections 29 and 28 from shaft 12 as a unit, thus giving access to clamping bolts 88 for the several collars and the clamping bolts M0 for the intermediate clamps. In the particular construction illustrated these bolts are inserted from the engine side of the spinner.

It will be evident that as a result of this invention a very simple and effective spinner supporting structure has been provided which is easily assembled and easily removed for purposes of access to the propeller. It will also be evident that a construction has been provided which is particularly adapted to provide the necessary support required for large diameter spinners; and that the construction not only provides a rigid support which accurately locates the spinner relative to the propeller shaft but that it also provides adequate reinforcement around the cutouts for the blade shanks.

While one embodiment of the invention has been shown and described herein it will be evident that various changes in the construction and arrangement of the parts may be made without departing from the scope of the invention as defined by the appended claims.

What it is desired. to secure by Letters Patent is:

1. In an airplane propeller assembly, a hub having radially extended blade shank receiving barrels, blades having their shanks extending into said barrels, extension sleeves secured to the free ends of said barrels, said sleeves having clamp locating mean accurately located with respect to the axis of rotation of the propeller, a spinner.

clamp locating means of said sleeves, one mem ber of each pair being connected to a shell section.

2. In an airplane propeller assembly, a hub having radially extended barrels, blades having different their shanks extending into said barrels, exten sion sleeves secured to the free ends of said barrels, said sleeves having peripheral clamp locating grooves adjacent their free ends accurately located with respect to the axis of rotation of the propeller, a spinner shell comprising a forward hollow cone section and an annular section forming an aft extension of said cone, said shell sections having complemental cutouts to receive said blade shanks, and means for connecting said shell sections detachably together including a pair of clamping members at each blade shank location having key portions received in said annular clamp locating grooves, one member of each pair of clamping members being connected to a different shell section, and means for clampings said pairs of members around said sleeves.

3. In an airplane propeller assembly, a hub having radially extended barrels, blades having their shanks extending into said barrels, extension sleeves secured to the free ends of said barrels, said sleeves having annular clamp locating grooves adjacent their free ends accurately located with respect to the axis of rotation of the propeller, a spinner shell comprising a forward hollow cone section and an annular section forming an aft extension of said cone, said shell sections being divided in a plane including the axes of said shanks and having completmental cutouts to receive said shanks, and means for connecting said shell sections detachably together and for supporting the same for rotation with said hub including a pair of clamping members surrounding said sleeves, one member of each pair being connected to a difierent shell section, said clamping members having arcuate key portions accurately fitting said clamp locating grooves, and fore and aft extending clamping means for connecting said clamping members.

4. In an airplane propeller assembly, a hub having radially extended barrels, blades having their shanks extending into said barrels, extension sleeves secured to the free ends of said barrels, said sleeves having annular clamp locating grooves adjacent their free ends accurately located with respect to the axis of rotation of the propeller, a spinner shell comprising a forward hollow cone section and an annular section form ing an aft extension of said come, said shell sections being divided in a plane including the axes of said shanks and having complemental cutouts to receive said shanks, and means for connecting said shell sections detachably together and for supporting the same for rotation with said hub including a pair of clamping members surrounding each of said sleeves, one member of each pair being connected to a different shell section and each of said members having key means received in said clamp locating grooves, pairs of parallel web members extending between and connected to said clamping members, means for connecting one web member of each pair of web members to a different shell section, and fore and aft clamping means connecting said pairs of clamping members and said pairs of web members.

5. In an airplane propeller assembly, a hub having radially extending barrels, blades having their shanks extending into said barrels, extension sleeves secured to the free ends of said barrels, said sleeves having clamp locating means at their free ends accurately located with respect to the axis of rotation of the propeller, a, spinner shell enclosing said hub, and clamping means carried by said shell and cooperating with the locating means on said sleeves for supporting said spinner.

6. In an airplane propeller assembly, a hub having radially extending barrels, blades having their shanks extending into said barrels, extension sleeves secured to the free ends of said barrels, said sleeves having clamp locating means at their free ends accurately located with respect to the axis of rotation of the propeller, a spinner shell enclosing said hub, said shell having fore and aft sections divided in a transverse plane including the axes of said blade shanks, and clamping means carried by said shell sections and cooperating with the locating means on said sleeves for supporting said spinner and detachably connecting said shell sections together.

7. In an airplane propeller assembly, a hub having radially extending barrels, blades having their shanks extending into said barrels, extension sleeves secured to the free ends of said barrels, said sleeves having clamp locating means at their free ends accurately located with respect to the axis of rotation of the propeller, a spinner shell enclosing said hub, said shell having fore and aft sections divided in a transverse plane including the axes of the blade shanks, clamping means carried by said shell sections and cooperating with the locating means on said sleeves for supporting said spinner and connecting said shell sections detachably together, and a conical nose section detachably secured to the forward periphery of said forward section for permitting access to said shell supporting means,

8. In an airplane propeller assembly, a hub having radially extended barrels, blades having their shanks extending into said barrels, extension sleeves secured to the free ends of said barrels, said sleeves having clamp locating means accurately located with respect to the axis of rotation of the propeller, a spinner shell comprising fore and aft sections divided in a transverse plane including the axes of said blade shanks, said shell having cutouts to receive said blade shanks, and means for detachably connecting said fore and aft sections including pairs of clamping members at the cut outs and also between said cut outs, one member of each pair being connected to a difierent shell section, and fore and aft extended clamping means for securing said members together, said clamping members at said cut outs having inwardly directed portions which surround the free ends of said sleeves and cooperate with said clamp locating means to position and support said spinner concentric with said propeller axis.

EDWARD W. RADTKE.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Number Name Date 1,978,039 Caldwell et al. Oct. 23, 1934 2,161,242 Benson June 6, 1939 2,194,890 Seversky Mar. 26, 1940 2,329,606 Goodman Sept. 14, 1943 2,371,801 Chester et al Mar. 20, 1945 

